基于欧拉方程的高超声速飞行器的壁面流线生成计算

Study and numerical calculation wall streamline distributions for hypersonic vehicle according to Euler equation

提出了一种新的利用表面流函数法计算高超声速飞行器表面流线分布的方法.首先提出了表面流函数的概念,并通过理论推导,得到了表面流函数与表面流线的关系;然后运用结构化网格求解三维Eu-ler方程,计算得到高超声速钝头体的边界层外缘外部无粘流场气流参数;最后利用无粘流场气流参数和表面流函数的方法计算了高超声速飞行器的精确表面流线分布.结果表明,在无攻角和攻角小于20°的情况下均可以得到较好的壁面流线分布.高精度的表面流线的得到,为利用边界层内粘性主导区域的积分方程等方法进一步精确预测高超声速飞行器表面的气动加热奠定了基础.

A new method for calculating the wall streamline distributions on hypersonic vehicles was presented. Firstly surface stream function was put forward, and the relationship between surface function with surface streamline was obtained. Secondly the boundary layer edge conditions were determined by 3-D CFD method and solved by 3-D Euler equtions. And finally, the wall streamline distributions were computed based on the stream function theory and flow parameters. The calculated results indicate that the prediction and the numerical simulation proposed are workable at small angle and without angle of attack. It will play an important role in exactly predicting the heating rates on hypersonic vehicles.